Multi-Stage Engine Bleed Air Extraction with Turbo-Compressor Heat Management
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Solution Overview
Problem
Existing aircraft environmental control systems waste energy by extracting high-pressure bleed air from engines, reducing efficiency, and require large turbo-compressors with drag-inducing atmospheric inlets prone to icing, increasing complexity and cost.
Innovation Solution
An engine bleed air system with taps for extracting air at multiple compressor stages, utilizing a turbo-compressor with a compressor and turbine, and heat exchangers to manage pressure and temperature, reducing energy consumption by extracting air at lower pressures and optimizing air delivery to environmental control systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high-pressure bleed air is extracted from the engine compressor, then the environmental control system can be supplied with sufficient pressurized air, but engine efficiency is significantly reduced due to energy waste in cooling the bleed air
Solution Approach 1:
The patent extracts bleed air at multiple compressor stages (both high and low pressure taps) rather than relying solely on high-stage extraction. This allows the system to take out only the necessary amount of air at appropriate pressure levels, reducing the energy penalty on the engine while still meeting the environmental control system's pressurization needs.
Solution Approach 2:
The patent combines high-pressure bleed air extraction with low-pressure bleed air extraction and merges them through a common bus system. This merging allows flexible distribution of air at different pressure levels to various aircraft systems, optimizing engine efficiency while maintaining sufficient pressurized air supply capability.
2Loss of energy
If a turbo-compressor with atmospheric inlet is used to reduce bleed air extraction, then engine efficiency is improved, but the system becomes more complex and costly due to required anti-icing systems
Solution Approach 1:
The patent uses the engine's existing compressor and bleed air system as an intermediary to provide pressurized air, rather than introducing a completely separate turbo-compressor system with atmospheric inlet. This approach leverages the existing engine infrastructure, avoiding the need for additional anti-icing systems and reducing overall system complexity while maintaining engine efficiency.
3Power
If a large turbo-compressor is used to produce sufficient pressure change, then the required pressure for aircraft systems can be achieved, but the atmospheric inlet produces drag
Solution Approach 1:
The patent provides different pressure levels at different locations (compressor stages) and extracts air locally where needed. By having multiple extraction points at various pressure levels, the system achieves the required pressure change capability for different aircraft systems without needing a single large atmospheric inlet, thereby avoiding associated drag penalties.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enhances engine fuel efficiency by minimizing energy draw from the engine and reducing system complexity and costs through controlled extraction and heat management, while avoiding icing issues.
Implementation Method 1
A bypass heat exchanger is arranged to remove heat from the bypass line
Implementation Method 2
A balancing heat exchanger is arranged to remove heat from the delivery line
Implementation Method 3
a turbo-compressor having a compressor and a turbine
Data Source
AI summary
An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.